EASA AD No : 2009-0058 

EASA Form 110 Page 1/3 

EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2009-0058 

Date: 13 March 2009 

Note: This Airworthiness Directive (AD) is issued by EASA, acting in accordance with 

Regulation (EC) No 216/2008 on behalf of the European Community, its Member States and of 

the European third countries that participate in the activities of EASA under Article 66 of that 

Regulation. 

This AD is issued in accordance with EC 1702/2003, Part 21A.3B. In accordance with EC 2042/2003 Annex I, Part M.A.301, the 

continuing airworthiness of an aircraft shall be ensured by accomplishing any applicable ADs. Consequently, no person may operate 

an aircraft to which an AD applies, except in accordance with the requirements of that AD, unless otherwise specified by the Agency 

[EC 2042/2003 Annex I, Part M.A.303] or agreed with the Authority of the State of Registry [EC 216/2008, Article 14(4) exemption]. 

Type Approval Holder’s Name : 

AIRBUS SAS 

Type/Model designation(s) : 

A310 Aeroplanes 

TCDS Number : France No 145 

Foreign AD : Not applicable 

Supersedure : None 

Note: This AD replaces the requirements of § 1.16 of EASA AD 2007-0053R1, which has been revised. 

ATA 53 Fuselage – Aft Fuselage Lower Tail Plane Cut-out – Inspection 

Manufacturer(s): Airbus (formerly Airbus Industrie) 

Applicability: 

Airbus A310-203, A310-203C, A310-204, A310-222, A310-304, A310-322, 

A310-324 aeroplanes models, all serial numbers, except aeroplanes that have 

received Airbus modification 06146 during production. 

Reason: 

A specific area, the lower tail plane cut-out located in the tail cone is subject to 

an inspection programme specified in the Airbus Service Bulletin (SB) A310-

53-2074. EASA issued AD 2007-0053 to require the accomplishment of this 

SB at Revision 03. 

Airbus has established that this SB needed to be revised in order to state 

correct threshold and intervals due to errors introduced at revision 03. 

Consequently, revision 04 of this SB has been issued, and opportunity was 

taken : 

- to clarify the inspection area and associated threshold and intervals 

- to take aeroplane utilisation into consideration, in accordance with the A310 

life extension programme. 

For the reasons stated above, this EASA AD takes over the requirements of 

paragraph 1.16 of EASA AD 2007-0053R1, which has been revised 

accordingly, and requires accomplishment of the instructions contained in 

Airbus SB A310-53-2074 at Revision 04. 

Effective Date: 27 March 2009 
EASA AD No : 2009-0058 

EASA Form 110 Page 2/3 

Required Action(s) 

and Compliance 

Time(s): 

Required as indicated, unless already accomplished : 

(1) No later than the threshold defined in Airbus SB A310-53-2074 at 

Revision 04, inspect the lower tail plane cut-out area in the tail cone and, 

depending on findings, apply corrective measures in accordance with 

Airbus SB A310-53-2074 Revision 04. 

Note 1: For aeroplanes previously inspected in accordance with Airbus SB 

A310-53-2074 revision 03, no further action is required by paragraph (1). 

(2) Thereafter, repeat the inspection at the intervals and according to the 

instructions defined in Airbus SB A310-53-2074 Revision 04 and, 

depending on findings, apply corrective measures. 

(3) For aeroplanes that, on the effective date of this AD, have already 

reached or exceeded the inspection threshold or interval, the respective 

grace period indicated in Table 1 of this AD can be applied, as applicable 

to aeroplane model and Short Range (SR) use, average flight time (AFT) 

equal to or less than 3.17 hours, or Long Range (LR) use, AFT exceeding 

3.17 hours. 

Note 2: To establish the average flight time, take the accumulated flight time 

(counted from the take-off up to the landing) and divide by the number of 

accumulated flight cycles. This gives the average flight time per flight cycle. 

Table 1 

Affected aeroplanes Grace period, whichever 

occurs first after the 

effective date of this AD 

A310-203, A310-203C, A310-204 and 

A310-222 aeroplanes that have 

exceeded the threshold by 16 500 

Flight Cycles (FC) or 33 000 Flight 

Hours (FH), or the applicable interval 

by 4 500 FC or 9 000 FH 

within 1 500 FC or 3 000 FH 

‘SR’ A310-304, A310-322 and 

A310-324 aeroplanes that have 

exceeded the threshold by 10 800 FC 

or 30 450 FH, or the applicable 

interval by 3 600 FC or 10 200 FH 

within 1 200 FC or 3 300 FH 

‘LR’ A310-304, A310-322 and 

A310-324 aeroplanes that have 

exceeded the threshold by 6 750 FC 

or 33 750 FH, or the applicable 

interval by 2 250 FC or 11 250 FH 

Within 750 FC or 3 750 FH 

(4) The application of corrective measures in accordance with Airbus SB 

A310-53-2074 revision 04 does not constitute terminating action for the 

repetitive inspection requirements of this AD. 

Ref. Publications: 

Airbus Service Bulletin A310-53-2074 Revision 03 or Revision 04. 

The use of a later approved revision of this document is acceptable for 

compliance with the requirements of this AD. 

Remarks :

1. If requested and appropriately substantiated, EASA can approve 

Alternative Methods of Compliance for this AD 

2. This AD was published on 13 January 2009 as PAD 09-014 for 

consultation until 03 February 2009. The Comment Response Document 

can be found at http://ad.easa.europa.eu/. 
EASA AD No : 2009-0058 

EASA Form 110 Page 3/3 

3. Enquiries regarding this AD should be referred to the Airworthiness 

Directives, Safety Management & Research Section, Certification 

Directorate, EASA; E-mail ADs@easa.europa.eu. 

4. For any question concerning the technical content of the requirements in 

this AD, please contact: Airbus SAS – EAW (Airworthiness Office, 

Telephone:+ 33 5 61 93 36 96, Fax:+ 33 5 61 93 44 51)